Aeroplane.



G. C. LOENING.

AEROPLANE.

APPLICATION FILED OCT. 31, 1nd.

1 ,Q@3,8@8@ iutent-ed Nov. 5, 1918.

3 SHEETSSHEET 2.

G. C. LOENING.

AEROPLANE.

APPLICATION FILED OCT. 31, me

Patented. Nov. 5, 1918.

3 SHEE1SSHEET 3.

A T TUE/V5 r.

GBOVJER CLEVELAND LOJENING, 0F BOSTON, MASSAGHUSETTS, ASSIGNOR 'I'O STUBTE- VANT AEROPLATNE COMPANY, OF JAMAICA PLAIN, MASSACHUSETTS, A GORPDRA- TION' OF MASSACHUSETTS.

AEROPLAN 1E.

Specification of lLetters Patent.

Patented Nov, 5, little,

. Application filed October 31, 1916. Serial No. 128,739.

To all whom it may concern:

Be it known that T, Grover CLEVELAND Lonnmc, a citizen of the United States, residin at Boston, in the county of Sufiolk and gtate of Massachusetts, have invented an Improvement in Aeroplanes, of which the following'description, in connection with the accompanying drawings, is a specification, like characters on the drawings representing like parts.

The invention to be hereinafter described relates to aeroplanes, and more particu larly to an improved radiator cooling system for the engine of an aeroplane.

Heretofore, the radiator has been located directly in front of the engine, back of and in axial alinement with the propeller Where it is partially shielded by the latter and out of range of the eflective aircool1ng currents; or it has been located at a side of the engine where it is. subject to ob ect1ona ble vibrations, presents excessive head resistance, is dificult to support, and is in the way 'of the pilot of the aeroplane.

The present invention aims to overcome the above and other objections to former constructions. To accomplish this, one object of the invention is to construct and arrange the' radiator to reduce head reslstance to the air. crease the cooling efiiciency of the radiator.

Another object is to locate the radiator within the range. of the energetic air cur rents developed by the propeller blades. Another object is to eliminate the vibrations of the radiator. Another object is to construct and arrange the radiator to prevent its obstructing the vision of the pilot. Still another object is to promote the circulation of the cooling water through the system.

The character of the invention may be best understood by reference to the following description of the embodiments thereof shown in the accompanying drawings, wherein g Figure 1 is a front elevation of a portion of an aeroplane equipped with a radiator engine cooling system embodying the 1nvention Fig. 2 .is a perspective view onan enlarged scale, of the parts shown in Fig. 1;

Fig. 3 is another erspectrve view ofthe radiator showing 1; e p1pmg connections therefor; and

Fig. 4: is a front elevation of an aeroprises an upper header 19 Another object is to in-,

plane and radiator construction, somewhat different from that shown in Figs. 1 to 3.

. Referring to the drawings: 1 and 3 in Fig. l designate the upper and lower main sustaining planes of an aeroplane of the seaplane type. These planes may be connected by vertical struts 5, stifi ened by diagonal guy wires 7. Pontoons 9 are provided heneath the planes for supporting the machine upon water, and'may be connected to the lower main plane by struts 11 stiflened by diagonal stays 13. A body 15 mounted centrally above the lower plane receives the engine which drives the propeller 17 and contains the cockpit for the accommodation of the pilot of the aeroplane, and passengers. The engine is provided with a water chamber for cooling the same, ofusual construction, and therefore unnecessary to illustrate herein.

Having described the general construc tion of the machine, next will be described the improved radiator cooling system embodying the invention. The radiator com- (Figs. 2 and 3), 1n the present instance, within the plane of the upper main sustaining plane, and preferably fitted into a recess21 in the advanclng edge of said plane. This header 19 may be shaped to conform to the contour of said plane, and constitute, in effect, a part thereof. v

A hollow til-shaped frame 23 may depend from the said header and contain the usual comb 25 providing an extended surface, re ticulated to permit the edective cooling action of the air thereon. A cap 26 at the top of the header, permits the introductionof water therein.

In the present instance of the invention, the-radiator is shown provided with piping for a Vengine, comprising two groups of cylinders. The hot water may be conducted from the jackets for the groups by inlet pipes 21 extending upward through the .cowl of the body in front of the. radiator comb and entering the under wall of an admay be distributed bythe latter to the comb and ravitate downward through the comb and be cooled in its transit therethrough. The cooled water is conducted therefrom back to the engine j acket's through the outlet pipes 29, having their. upper ends entered into the base of the radiator frame. These water circulation pipes may be in sections connected by rubber .unions 31 clamped thereto 'for preventing transmission of engine vibrations to the radiator.

To secure the radiator in position, its header may have angle brackets 33, Fig. 2, on the rear edge thereof bolted to brackets 35 on the main plane, and its U frame may have brackets 37, Fig. 3, on the base thereof, connected by the clips 39 with the upwardly converging struts 41 -having their lower ends securedtothe body fuselage at the rear of the cowl, and their upper ends secured to the upper .main sustaining plane. These struts may serve as a backing for the radiator and cooperate with the upper main plane to hold the radiator rigidly in position without vibration.

-In Fig. 4=is shown an aeroplane of simi-' lar construction, but somewhat different proportions from the aeroplane shown in Figs. 1 to 3, and equipped with a radiator 43 similar' to the one first described, but with the exception that it "is longer, narrower,

projects a shorter distance beneath the upper main plane, and its inlet and outlet pipes 45 and 47 proj ect vertically upward in registration with the struts 51 extending between the fuselage and the upper main plane; This tandem arrangement of the struts and pipes reduces head resistance to the air, provides a strong, compact construction, and forms a desirable stream line construction. j I

There are important advantages in the radiator constructed and arranged as described. I

The upper header of the radiator essentially must have a substantial front area in order to supply and distribute the water to the comb beneath it, but this area, instead of ofiering head resistance, constitutes, in

effect, a part of the main sustaining plane,

and serves the dual function of accommodat ing water for the radiator, and contributing to the support of the aeroplane. The U- frame containing the comb presents merely a very narrow edge to the air, and does-not ofier material headresistance. Thus, substantially the only portion of the radiator which is exposed to the air currents, is" the comb portion of the radiator, but this portion being reticulated, permits the air to readily pass therethrough. Therefore, a

' radiator is provided which is highly effective in cooling the water, but without material head resistance to the air.

Since the radiator is long and narrow, it may lie closely ad acent to the under surface of the upper main' plane in a position where it can receive and be efi 'ectively cooled by the energetic air stream compressed by said plane. The advance edge of the radiator header projecting somewhat beyond the comb, desirably contributes to the compression and direction of the air stream to the comb.

The long, narrow radiator projecting merely a slight distance beneath the upper main plane, is well up out of the way of the pilot and does not offer any obstruction to his view. Since the header is located well up a substantial distance from the engine,

with pipes of substantial length connecting them, the hot water will naturallytend to rise in the'inlet pipes, and the cold water will naturally tend to fall in the outlet pipes. Thus, there is provided a thermosiphon effeet which will desirably assist the pump in the system in maintaining the circulation of water through the 'system.

The fitting of the radiator head into the recess of the main plane and the securing of the U-frame to the stiif struts back of the radiator, eflectively prevents vibrations thereof.

What is olalmed is 1. In an aeroplane, the combination with header forming a partof said plane and" a reticulated portion projecting beneath said plane, a water inlet pipe communicating withsaid header, and a water outlet pipe communicating with said reticulated portion.

4. In an aeroplane, the combination with a main sustaining plane and a strut therefor, of an engine coolin system including a radiator having a head of said plane, and an air exposed cooling portion projectingbeyond said plane, and

' water circulation pipes communicatin with said radiator and registering with sai strut to diminish head resistance to the air.

5. In an aeroplane, the combination with a main sustaining plane, of an engine support, struts extending between said plane and support, a coolin system for the engine ineludin a radiator aving a header in the plane 0 said sustaining plane, an air exposed cooling portion projecting beyond said plane, and water circulation pipes communicating with said radiator and registering with said struts.

6. In an aeroplane, the combination with er forming a part naaaeaa upper and lower main sustaining planes, of an engine cooling system including aradia tor having a header in the plane of one of said sustaining planes, an air exposed cooling portion projecting beyond said plane, struts connected to the latter, means for securing the radiator to said struts, and piping registering with said struts for conductin water to and from said radiator.

In an aeroplane, the combination with a main sustaining plane, of an engine cooling system including a radiator having an air cooling portion projecting beneath said plane, and a header formed to conform to the contour of said plane and presenting a plane section for compressing and directing a cooling air stream to said air cooling portion. z

8. Inv an aeroplane, the combination with a main sustaining plane having a recess therein, of a radiator comprisin a header with a reticulated portion depending therefrom, said header being mounted in said recess and having an advance edge portion projecting beyond said reticulated portion to deflect the air thereto, and means to contherein, of a'radiator comprisinga header set into said recess, a hollow frame depending from said header and plane, a hollow reticulated structure mounted in said frame, 1

and means to conduct water to and from. said radiator.

10. In an aeroplane, the combination with a main sustaining plane having a recess therein, of a radiator comprising a header set into said recess and secured to said plane, a reticulated portion projecting from said header and plane and exposed to the air stream passing said plane, and means to conduct Water to and from said radiator.

In testimony whereof, I have signed my name to this specification.

GROVER @LEVELAND LOJENING. 

